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NASA NTRS · 20210026187

Mars Landing Vehicles: Descent and Ascent Propulsion Design Issues

Bryan Palaszewski
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Abstract

Human and robotic Mars missions often include plans for landing large payloads on the planet’s surface. Thus far, landing of payload of up to approximately 1 metric ton (MT) have been successful. Future human missions have suggested large 5 to 25 MT surface payloads may be needed. Therefore, large landing vehicles with an initial mass of up to 100 MT may be required. In this chapter, the future human payload missions are assessed, investigating the mission velocity changes (delta-V) values for deorbit, deceleration, landing and ascent. The initial masses of single and multi-stage Mars landing vehicles are computed. Issues related to vehicle mass factors and delivering the needed delta-V are discussed.

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MarsLandingChemical propulsionDescentDeorbitDecelerationHoverAscentIn-situ resource utilizationOrbital transfer

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Bryan Palaszewski. 2022-02-04. Mars Landing Vehicles: Descent and Ascent Propulsion Design Issues. https://ntrs.nasa.gov/citations/20210026187

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